RADIOSS - Composite Materials & Optimization

2015 European Altair Technology Conference
September 29 to October 1 | Paris
Technical Seminar
RADIOSS
Composite Materials & Optimization
Pierre-Christophe Masson – pcmasson@altair.com
Jean-Baptiste Mouillet – jbmouillet@altair.com
Juan Pedro Berro Ramirez – jpbramirez@altair.com
Erwan Mestres – emestres@altair.com
Vincent Diviné – vdivine@altair.com
Join, Contribute, Exchange
See full agenda at www.altairatc.com/europe

Copyright © 2013 Altair Engineering, Inc. Proprietary and Confidential. All rights reserved.
Abstract
Lightweight Design has always been important for some manufacturers
but today, it is becoming increasingly essential to fit the future resource
efficiency and emission standard requirements.
Optimization & Composite materials are two strategic keys to develop
lightweight designs. However, their applications to highly non-linear
analyses, such as crash and impacts, are quite complex topics.
This workshop will showcase the abilities regarding Optimization &
Composite with RADIOSS, the Altair solver for highly non-linear
analyses, how to setup and review composite models, how to perform
and optimize Composites parts using RADIOSS.»

01 Composite Initialization
02 Fluid Modeling
03 Post Processing of Composite Materials
04 Optimization
05 User Failure Criteria
RADIOSS
Composite Materials
& Optimization

About RADIOSS
Structural analysis solver for highly non-linear problems under dynamic
loadings.
• High Scalability, Quality and Robustness
• Supports multiphysics simulation and advanced materials
• Used across all industries to improve crash, safety and manufacturability
• For 20+ years an established standard for automotive crash and impact

RADIOSS : The Standard behind Structure Safety
Multiphysics Analysis
Crash and
Safety
Drop &
Impact
Blast &
Hydrodynamic
Impact
Fluid-
Structure
Interaction
Terminal
Ballistic
Forming &
Composites
Mapping
and Optimization

RADIOSS: Overview within HyperWorks
HyperWorks
HyperMesh
Meshing
Pre-Processing/Model Checker
HyperCrash
Pre-Processing/Mapping
Model Checker
RADIOSS
Analysis of highly Non Linear problems
under Dynamic loadings
HyperView/HyperGraph
Post-Processing
HyperWorks Partners
CAD & Mfg Interoperability
OptiStruct
Optimization (ESLM)
…
HyperStudy
DOE, Optimization, Robustness studies
HyperForm
Forming

RADIOSS Composite Modeling
New Stack & Ply possibility
Orientation Review
Composite Forming
Preliminary Optimization
01 Composite Initialization

Composite Zone-Based Modeling
position PART 1 PART 2 PART 3 PART 4 PART 5
1 Ply 0° Ply 90° Ply 45° Ply 90° Ply 0°
2 Ply 0° Ply 0° Ply 90° Ply 0° Ply 0°
3 Ply 0° Ply 0° Ply 0°
4 Ply 90° Ply 0° Ply 90°
5 Ply 90°
6 Ply 45°

Composite Ply-Based Modeling1Laminate
PLY 1 Ply 45°
PLY 2 Ply 90°
PLY 3 Ply 0°
PLY 4 Ply 0°
PLY 5 Ply 90°
PLY 6 Ply 45°

Composites Technology - Ply Based Modeling
A Composite Part is made up of “n” Plies and One Laminate
No Data Duplication
Direct Relationship to the Manufacturing Process
Ply Based Modeling Process
Define Ply Shapes and Related Ply Data
Define Stacking Sequences
Design Change Requires only 1 Update
P1 45
P2 90
P3 -45
P4 0
P6 90
P7 45
P5 -
45
Stack Table
Ply Mat Thk Theta
P7 M1 0.01 45
P6 M1 0.01 90
P5 M1 0.01 -45
P4 M1 0.01 0
P3 M1 0.01 -45
P2 M1 0.01 90
P1 M1 0.01 45

Property sets for Composite Modeling
Orthotropic Shell: TYPE9 SH_ORTH
Composite Shell: TYPE10 SH_COMP
Sandwich Shell: TYPE11 SH_SAND
Ply-based Sandwich Shell:
TYPE17 STACK
TYPE19 PLY
Composite Thick Shell:
TYPE22 TSH_COMP
Orthotropic Solid: TYPE6 SOL_ORTH
General Solid: TYPE14 SOLID
Sandwich Shell: /PROP/TYPE11
(SH_SAND)
• 4 and 3 nodes sandwich shell
elements
• N layers with
• Orthotropic layers (two directions)
• Different orientation of each layer
• Unequal thickness of layers
• Different materials for layers
• Material law can be :
• Law 25 (composite shell)
• Law 27 (brittle elastic plastic)
• Law 36 or 60 (tabulated piecewise
non linear elastic-plastic)
• User’s laws
• Same material law type for the
property

Property set for shell elements
Sandwich Shell: /PROP/TYPE11 (SH_SAND)
• Example
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/PROP/SH_SANDW/1
Composite_L7_UD
# Ishell Ismstr Ish3n Idril
12 0 0 0
# hm hf hr dm dn
0 0 0 .1 0
# N Istrain Thick Ashear Ithick Iplas
7 1 2.5 0 0 1
# Vx Vy Vz Skew_ID Iorth Ipos
1 0 0 0 1 0
# Phi t Z mat_ID
0 .5 0 11
45 .25 0 11
-45 .25 0 11
90 .5 0 11
-45 .25 0 11
45 .25 0 11
0 .5 0 11
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
Number of Layers
Total Thickness
Reference Orientation
Plies Definitions

Composite Material : /MAT/LAW25 (CRASURV)
Model
• Linear elastic behavior until the yield stress value followed by a plastic behavior
• Lamina yield surface is the TSAI-WU yield criteria function
• Plastic hardening function of plastic work defined independently for each direction
• Strain rate dependency
• Residual stress value after stress damage (without element deletion)
• Failure model in tensile, maximum plastic work and Tsai-Wu criteria.
• Composite fabric or fibers in the plane 12.
Elements
• Solid, Thick-shell and Shell elements.

Stack & Ply properties for shell elements
Ply-based Sandwich shell: /PROP/TYPE17 (STACK)
• Sandwich 4 and 3 nodes shell elements
• Layer is defined by plies
• Ply information: /PROP/TYPE19 (PLY)
• Material Law 25, 27, 36 or 60.
• Direction
• Thickness
• Inter-ply material (not yet active)
• Advantage :
• Continuity of the ply, even if the total number of plies changes in terms of geometry.
Stack = a “stack of plies”

Stack & Ply properties for shell elements
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/PROP/TYPE17/1
outer
# Ishell Ismstr Ish3n Idril
12 0 0 0
# hm hf hr dm dn
0 0 0 .1 .1
# N Istrain Thick Ashear Ithick Iplas
3 0 0,0000 0 1 1
# VX VY VZ skew_ID Iorth Ipos
0 0 1 0 0 0
# Pply_IDi PHIi Zi
1 0 0
# Mint_IDi
200
# Pply_IDi PHIi Zi
2 90 0
# Mint_IDi
200
# Pply_IDi PHIi Zi
3 0 0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/PROP/TYPE19/1
outer1
# mat_ID_i t delta_phi
13 1.0 0 1112
/PROP/TYPE19/2
outer2
13 1.0 45 1114
/PROP/TYPE19/3
outer3
13 1.0 0 1112

Comparison between OS input and RADIOSS input
$HMNAME LAMINATES 1"outer"
$HWCOLOR LAMINATES 1 5
STACK 1 1 2 3
$$
$
+ 3
$
/PROP/TYPE17/1
outer
…
# Pply_IDi PHIi Zi
1 0 0
# Mint_IDi
# Pply_IDi PHIi Zi
2 90 0
# Mint_IDi
# Pply_IDi PHIi Zi
3 0 0
$HMNAME PLYS 1"outer1"
$HWCOLOR PLYS 1 57
PLY 1 13 1.0 0.0 YES
+ 1112
$
$HMNAME PLYS 2"outer2"
$HWCOLOR PLYS 2 21
PLY 2 13 1.0 45.0 YES
+ 1114
$
$HMNAME PLYS 3“outer3"
$HWCOLOR PLYS 3 61
PLY 3 13 1.0 0.0 YES
+ 1112
$
/PROP/TYPE19/1
outer1
13 1.0 0 1112
/PROP/TYPE19/2
outer2
13 1.0 45 1114
/PROP/TYPE19/3
outer3
13 1.0 0 1112
OS RADIOSS

Global material
 Global material properties are now automatically calculated
 Equivalent material based on the properties of the layup
 Membrane
 Bending
 A material for part definition is still needed
(for pre and post treatment)
 The stability condition is recomputed
 Offset layup stability is improved
 Results may be changed within numerical sensitivity of the model
 Default option in v14, but it is possible to “go back”

 Order of the Stacking:
Layers are stacked
• from bottom to top
• from first layer to last layer
In HyperMesh:
Mesh > Check > Elements > Normals
Normal Orientation

Elementary System
Display of Element r,s,t vectors
Can be used to Check Normals
Or (r,s) system,
especially for solid elements
HyperMesh
HyperCrash

Check of Material Orientations
Display of Material Orientations (in HyperCrash)
Material Orientations

Initialization of Orthotropy Direction
Display of the initialization of orthotropy
direction for shells element (in
HyperCrash)
• Angle of first direction of orthotropy relatively of
first direction of the local reference frame
(/INISHE/ORTH_LOC)
• Angle for first axis of orthotropy relatively to
given reference vector (/INISHE/ORTHO)

Composite Forming
Aims:
1) To provide a simple solution which gives tendencies
• Simple set up with reduced numbers of input data
• Accurate enough to give main tendencies
• Fast enough to be used in an industrial context
2) Seamless crash model initialization with forming results
Solutions:
 One Step solutions: Drape Estimator
 Multi Scale methods (MDS, KTex (CEDREM))
 Incremental Computations

HyperForm/Incremental RADIOSS
Sandwich approach
 One part of shell elements with
• One composite material
• One multi-layers property
 To give tendancies
 No sliding between layers
 No coupling between warp and weft
directions
Independant Layers approach
 N parts of shell elements
• One material law per layer
• One property per layer
• Contact between layers
 More accurate
 Sliding between layers
 Coupling between warp and weft
directions
Sandwich approach Independant Layers approach
s11 s11
~
2 modeling approaches

Crash Model Initialization Process
1. Forming Setup:
• Die, Binder, Punch & Blank
2. Composite Setup:
3. Computation (RADIOSS)
4. Mapping
Approach Selection: Dry or Resin
Stacking definition
Ply creation
Material Orientation are mapped on the
different layers
2nd Directions can be mapped for Fabric
Blank type selection  Composite
Blank config selection  Multilayered
Automatic Creation of
• Contact interfaces tools and blank(s)
• Contact interface between layers
• Post-treatment cards in engine

Forming influence on Impact
Reference Model
Model initialized with fiber directions

Preliminary Optimization
Aims: Quickly Define Composite Patches before Performance Optimization
Solution:
 Run OptiStruct Free Size optimization
 Convert OptiStruct result to RADIOSS

Load Linearization
Identification of the most important force peaks
Forces extraction from RADIOSS Simulation Result using HyperView

Equivalent OS Model Set Up
MAT 8
1 PCOMPP & Laminate on each face
Each laminate composed of 4 plies
[0, 90, 45, -45]
3 Load collector corresponding for
each force’s peak
Inertia RELIEF active

Force Import: ANALYSIS  FORCES

One Design Variable (freeSize) for each laminate
Pattern repetition to get the same result on each face
Loading is not symmetric
Master
Master
Slaves
Slave
Objective
Min Compliance
Constraint
Vol Frac < 50%

Optimization Result
Freesize
Total thickness
Ply 0° Ply 90°
Ply 45° Ply -45°

Optimization Result
OptiStruct output fem

Conversion to RADIOSS
Using OptiStruct Non Linear analysis (NLGEOM, EXPDYN),
OptiStruct model is converted into RADIOSS input deck
(Bulk to Block conversion)
• OS Laminates are converted into STACK properties (TYPE 17)
• OS Plies are converted into PLY properties (TYPE 19)

SPH Modeling
ALE Modeling with Multiphasic Law
02 Fluid Modeling

Modeling the fluid: main difficulties
 Meshing:
• The volume may be difficult to mesh with Hexas
• Connect the tank to the fluid
 Stability
• High deformations of the fluid
 Solutions :
• SPH
• ALE

Why SPH?
 Domain divided by a set of particles tied to their neighbors
by internal forces
 Lagrangian approach:
• Physical laws of mechanics of continuum medium
• Material characteristics, velocity and mass assigned to the particles
• Interpolation and weight functions for interactions
 At each cycle, the “connectivity” changes
according to material deformations:
 No bad element shape
• Less error due to hourglass
• Less time step problem

SPH model
 Particle network
• Pitch = 5 mm
• Cubic centered network
 Connexion between tank and fluid
• Type 7 interface
• Gap = 2.5 mm
• Everything else = default value

SPH model

Why ALE?
 Multiphasic law 51 allows to model air
entrapment
 Faster than SPH (CPU/element is around 5-6)
 Robust method
• Insensitive to fluid deformation

ALE Features
 Fluid and structural mesh are not coincident
• Connexion through type 1 interface
• Reference with coincident mesh
 Free surface defined with /INIVOL
 Grid Mesh control
• Option /STANDARD
 Antidiffusion techniques
• SUPG
• Phase antidiffusion parameters

ALE model

ALE model: coincident vs non coincident mesh

Comparison ALE vs SPH
In the SPH model, the particles are not initially in uniform contact with the
tank
 2 pressure waves:
1. Tank vs ground
2. (Tank + fluid) vs ground

Comparison ALE vs SPH
SPH signal was shifted by 0,2 ms to take into account double shock

Comparison ALE vs SPH: synthesis
 SPH
• Simplicity
• Higher time step
 ALE
• Smooth contour pressure
• Interaction fluid vs tank
• CPU / cycle

Material Orientation
Failed Layers
Damage
03 Post Processing
of Composite Materials

Composite Material Post-Processing
Time History
• /TH/EMIN, /TH/EMAX – plastic work
• /TH/WPLAY_.... plastic work for each layer
• Element stress (element coordinate system)
Animation
• /ANIM/ELEM/EPSP/ALL – plastic work
• /ANIM/SHELL/TENS/STRAIN/ALL – strain tensor (global CS)
• /ANIM/ SHELL/TENS/STRESS/ALL – stress tensor (global CS)
• /ANIM/SHELL/FAIL
• /ANIM/SHELL/PHI/ALL – angle between first element direction and first fiber
direction
• /ANIM/BRICK/ORTHDIR/ALL – Euler angles (, , )
• /ANIM/SHELL/DAMA/ALL (new in v.14)
• /ANIM/BRICK/DAMA/ijk (new in v.14)

Post Processing RADIOSS Composites
Direct Post Processing

Failed Layers
Understanding rupture process

Failure Model Damage Value
Johnson-Cook failure
Tuler-Butcher failure
Wilkins failure
BAO-XUE-Wierzbicki failure
Strain Failure Model with dependence on Lode angle
FLD failure
Strain failure
Specific energy failure
CHANG failure
HASHIN composite failure
PUCK failure
NXT Failure
Damage Visualisation – D value definition
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or
ormajor
time
MaxD
minlim
min
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MaxD

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 dmcf eeeeMaxD ,,,
 4321 ,,, FFFFMaxD 
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/ANIM/SHELL/DAMA : understanding failure process
Max damage over layers Damage, layer 1
Damage, layer 8

/ANIM/SHELL/DAMA : understanding failure process
Max damage over layers Damage, layer 1
Stress tensor
Compression « vertical direction »
is critical

Overview of Equivalent Static Load Method
ESLM in RADIOSS or Optistruct
RADIOSS block optimization keywords
Example optimization
Other?
04 Optimization

Equivalent Static Load Method
• Considering time history and not just worst case time step
ft
eq = Kdt
t
d
OptiStruct
Analysis
Dynamic / Nonlinear Problem
Load time history
Optimization
Static Response Problem
Equivalent static loads
Load
Design variables

Nonlinear Response Optimization
• Contact Nonlinearity (NLSTAT)
• Implicit solution
• Contacts are updated at each optimization iteration
• Linear geometry solution
• ESLM-based Geometric Nonlinearity (NLGEOM, IMPDYN, EXPDYN)
• Implicit and explicit solutions
• Gradients can be very expensive or unavailable
• Equivalent static load method: representing the nonlinear problem into a series of
linear problems
• More efficient
• Existing optimization techniques (for linear problems) can be used

Equivalent Static Load Method
• Nonlinear analysis (outer loop), Static optimization (inner loop)
• will be determined in order to reach the same response field as
nonlinear analysis (including dynamic effects)
ft
eq = Kdt
Start
Calculate equivalent
static loads
Converged
No Yes
Stop
Update design
variables Load set feq0 feq1 feq2  feqn
Time Step t0 t1 t2  tn time
displacement
Solve static response
optimization
Nonlinear
Analysis

ESLM Workflows
OptiStruct Syntax
RADIOSS Syntax (new in v13)
• RADOPT

Solver Integration, RADIOSS block input format
OptiStruct reader
Build RADIOSS model
Run RADIOSS solver
Calculate ESLM loads
and linear subcases
Linear optimization
(inner loop)
Inner loop converges with
updated desvars
input.rad (optimization)
input_0000.rad (starter)
input_0001.rad (engine)
Outerloop
conv
No
Stop
Yes
input.fem (ESL-B2B)Created by
Optistruct

Capabilities
Design variables:
• Shape / Freeshape;
• Size (shell thickness, beam section area etc)
• Free-size optimization (composites are not supported);
• Topology optimization (composites are not supported)
• Topology optimization for solids in (v 14.0)
Responses:
• Displacement
• Strain(including plastic strain)
• Stress
• Internal energy
• Volume/mass
• Velocity (v. 14)
• Acceleration (v. 14)

Input design (similar as OptiStruct cards)
Objective
• /DESOBJ
Constraints
• /DCONSTR
Responses
• /DRESP1
• /DRESP2 (v 14.0)
Design variables
• /DESVAR, /DSIZE, /DTPL, /DTPG, /DSHAPE, /DVGRID
Relate design variable with properties
• /DVPREL1
Equations
• /DEQATN (v 14.0)

/DESOBJ
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DESOBJ
myobj-
# type resp_ID
0 1
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
 This keyword can be used to select a response as the objective function
 The selected response can either be minimized or maximized based on
the inputs specified on this keyword.
 Only one objective can be defined for an optimization run.
 Type:
 0: The selected response function is minimized
 1: The selected response function is maximized

/DCONSTR
 Constrains a design response by specifying its lower and upper
bounds.
 Cmin: Lower Bound for the constrained response
 Cmax: Upper Bound for the constrained response
 Unnecessary bounds should be left blank (& not 0)
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DCONSTR/1
disp constraint
# resp_ID cmin cmax
2 19.7742
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

/DRESP1
 Defines a response or a set of responses that are a result of a design
analysis iteration
 They can be used as a design objective or as design constraints
 Types: Mass, Volume, Displacement, Stress, Strain, Internal Strain
Energy
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DRESP1/1
min mass
# RTYPE PTYPE REGION ATTA ATTB ATTI
# mass part grpart
1 3 1 2000329
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DRESP1/2
disp19.7742mm
# RTYPE PTYPE REGION ATTA ATTB ATTI
disp node dir grnod
5 1 2 2021524
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

/DRESP1 - Optimization Design Response, continued

/DESVAR
 Optimization Design Variables
 Xini: Initial Value
 Xmin: Lower Bound
 Xmax: Upper Bound
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DESVAR/1
design variable for thick mid reinforcement
# Xini Xmin Xmax
0.7 0.5 3.0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DESVAR/2
design variable for thick for inside reinforcement
# Xini Xmin Xmax
0.7 0.5 3.0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

Optimization Design Variables
See online help for details about each design variable
Keyword Description
/DSIZE Free-Size Optimization
/DTPL Topology Optimization
/DTPG Topography Optimization
/DSHAPE Free-Shape Optimization
/DVGRID Size Optimization

/DVPREL1
 Relates Design Variables to Analysis Model Properties
 Property Type:
 1: /PROP/SHELL  prop_fid: 1 = thickness
 2: /PROP/TRUSS  prop_fid: 2 = area
 3: /PROP/BEAM  prop_fid: 1 = area, 2 = Iyy, 3 = Izz, 4 = Ixx
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DVPREL1/1
link_dv_shell_T for mid reinforcement
# prop_typ prop_id prop_fid C0
1 2000329 1 0.0
# DVid1 COEF1
1 1.0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|
/DVPREL1/2
link_dv_shell_T for inside reinforcement
# prop_typ prop_id prop_fid C0
1 2000327 1 0.0
# DVid1 COEF1
2 1.0
#---1----|----2----|----3----|----4----|----5----|----6----|----7----|----8----|----9----|---10----|

/ESLPART – specify parts for ESL optimization
By default, the entire RADIOSS model is used in constructing the
OptiStruct ESL optimization model.
With /ESLPART
• Specify part of the RADIOSS model to be used in ESL optimization;
• The full RADIOSS model is still used in analysis and design validation
(with the optimized part updated).

Example
SHELL property (PROP/TYPE1)
with isotropic material
Objective
Min MASS
Constraint
Stress < 450MPa
Manufacturing
Constraints
Cyclic Symmetry

Example
RADOPT Card
Tank wall ID
Response definition
Variable bounds
Stress Constraint
Mindim
Cyclic
Sym

Example
Cyclic symmetry definition

Example
Result
6 Optimization Loops

DOE
Opt
RBDO
Coupling HyperStudy & RADIOSS
• When Optimization must take in account highly non linear phenomena:
• Post rupture behavior
• Post buckling behavior
• Size/Morphing Optimization using HyperStudy
• Infinite Exploration with HW Unlimited
OS
Patch
identification
RADIOSS
Full Non Linear

User Process
Application to Composite Materials
05 User Failure Criteria

Failure Models in RADIOSS
Type Description Keyword /FAIL
Chang-Chang Failure criteria for composites /CHANG
Failure Normal & Tangential for connectors /CONNECT
Specific energy Specific energy /ENERGY
FLD Forming Limit Diagram /FLD
Hashin Composite model /HASHIN
Johnson-Cook Ductile failure /JOHNSON
Ladeveze delamination Composite delamination /LAD_DAMA
NXT Similar to FLD, but based on stresses /NXT
Puck Composite model /PUCK
Spalling & Johnson-Cook Ductile and spalling /SPALLING
Strain failure Damage accumulation using user functions /TAB1
Tuler-Butcher Failure due to fatigue /TBUTCHER
Tensile Tensile strain failure /TENSSTRAIN
Bao-Xue-Wierzbicki Ductile material /WIERZBICKI
Johnson Cook XFEM Johnson-Cook with XFEM /XFEM_JOHNS
Failure models are independent and can be coupled with compatible material

User Subroutines in dynamic library
 Available for :
 user windows
 user material laws
 user failure criteria
 user properties
 user sensors
 Compilation procedure is easy and independent from RADIOSS version
 No need to re-link for each RADIOSS version
 dynamic libraries are “small” and can be delivered easily to clients
 Very easy to manipulate

The RADIOSS Userlib SDK – Generate the dynamical library :
libraduser_linux64.so / libraduser_win64.dll
Located in HyperWorks : hwsolvers/radioss/userlib_sdk
 Available on Linux & Windows
 2 Compilers for each OS
 INTEL COMPILER (Recommended)
 Open Source compiler (since Radioss 14)
GNU Fortran – Linux
• MinGW – Windows
 SDK contains :
 Compiling Scripts
 Some Interface libraries
Needed to generate the Library
Set 2 Environment variables & invoke the Script :
RAD_USERLIB_SDK_PATH : Sdk Root name
RAD_USERLIB_ARCH : OS & Compiler choice
*********************************************
** Generating Radioss Dynamic User Library **
*********************************************
Preparing Library
-----------------
Compiling: lecm29.F
----------
lecm29.F
Compiling: sigeps29c.F
----------
sigeps29c.F
Creating library: libraduser_win64.dll
----------------
Creating library libraduser_win64.lib and object
libraduser_win64.exp
Done
----

Radioss Starter and Engine load the library if available !
Location is either:
 RAD_USERLIB_LIBPATH (RADIOSS V14)
 Local Directory (RADIOSS V14)
 LD_LIBRARY_PATH (Linux) / PATH (Windows)
Or can be loaded with –dylib
command line option (RADIOSS V14)
 This option permits to use an alternate library name.
When library is successfully loaded,
 Library information is printed in out files.
 When Dataset contains User Carts, Routines in the Library are invoked
EXTERNAL LIBRARY FOR USERS CODE INTERFACE
-----------------------------------------
LIBRARY NAME . . . . . . . . . . . . . . . . . libraduser_win64.dll
RADIOSS USERS CODE INTERFACE VERSION . . . . .1301501260
RADIOSS
Libraduser_win64.dll

How to use the dynamic library?
Move the dynamic library in the model directory
Or copy your dynamic library to your RADIOSS install directory:
HW_Installation_directoryhwsolversbinwin64
Note : if there are dynamic libraries in both directories, the RADIOSS install directory ones
have priority.

Failure criteria
 3 user failure criteria are available
• /FAIL/USER1
• /FAIL/USER2
• /FAIL/USER3
 3 subroutines / failure criteria :
• Lecr04 : starter, USER1
• f04law : solver calculation solids (USER1)
• f04lawc : solver calculation for shell (USER1)
• 05 for USER2, 06 for USER3
 Very similar to user material laws (variable names …)

Example: Orthotropic failure strain
12
/FAIL/USER1/32
# eps1ini eps1f
.01 .012
# eps2ini eps2f
.01 .012
# eps12ini eps12f
.10 .15
 Purpose :
 Degradation and possible deletion of element as a function of several variables
(stress, strain, user variables …)

SUBROUTINE LECR04 (IIN ,IOUT ,UPARAM ,MAXUPARAM,NUPARAM,
1 NUVAR,IFUNC,MAXFUNC,NFUNC)
Variable declaration
READ(IIN,"(2F20.0)")eps1ini,eps1f
NUPARAM = 6
UPARAM(1) = eps1ini
UPARAM(2) = eps1f
UPARAM(3) = eps2ini
UPARAM(4) = eps2f
UPARAM(5) = eps12ini
UPARAM(6) = eps12f
WRITE(IOUT, 1100)
WRITE(IOUT, 1100) eps1ini,eps1f
WRITE(IOUT, 1200) eps2ini,eps2f
1000 FORMAT(
& 5X,' USER ORTHOTROPIC FAILURE CRITERIA',/,
& 5X,' --------------------------------- ',//)
1100 FORMAT(
& 5X,'STRAIN THRESHOLD FOR DIRECTION 1. . .=',E12.4/,
& 5X,'STRAIN MAX FOR DIRECTION 1. . . . . .=',E12.4/)
1200 FORMAT(
& 5X,'STRAIN THRESHOLD FOR DIRECTION 2. . .=',E12.4/,
& 5X,'STRAIN MAX FOR DIRECTION 2. . . . . .=',E12.4/)
1300 FORMAT(
& 5X,'STRAIN THRESHOLD FOR DIRECTION 12 . .=',E12.4/,
& 5X,'STRAIN MAX FOR DIRECTION 12 . . . . .=',E12.4/)
RETURN
END
 Starter: lecr04
 read input file (0.rad)

SUBROUTINE (
1 NEL ,NUPARAM ,NUVAR ,NFUNC ,IFUNC,NPF,
2 TF ,TIME ,TIMESTEP ,UPARAM ,NGL ,IPT,
3 NPT0 ,NOT_USE_I1,NOT_USE_I2 ,NOT_USE_I3,
4 SIGNXX ,SIGNYY ,SIGNXY ,SIGNYZ ,SIGNZX ,
4 EPSPXX ,EPSPYY ,EPSPXY ,EPSPYZ ,EPSPZX ,
6 EPSXX ,EPSYY ,EPSXY ,EPSYZ ,EPSZX ,
7 PLA ,DPLA ,EPSP ,UVAR ,UEL ,
8 OFF ,NOT_USED1 ,NOT_USED2,NOT_USED3,NOT_USED4,NOT_USED5 )
Variable declaration
eps1ini = UPARAM(1)
eps1f = UPARAM(2)
eps2ini = UPARAM(3)
eps2f = UPARAM(4)
eps12ini = UPARAM(5)
eps12f = UPARAM(6)
DO I =1,NEL
IF((OFF(I).EQ.1.0 ).AND. (EPSXX(I).GE.eps1ini)) THEN
d11(I) = (EPSXX(I) - eps1ini ) / (eps1f - eps1ini)
d11f(I) = min(1.0 , d11(I))
SIGNXX(I) = (1.0 - d11f(I))*SIGNXX(I)
ENDIF
Same for directions 12, 22
ENDDO
C
RETURN
END
 Engine : f04law (for solid elements)

 Engine : f04law (for solid element deletion)
C Total Failure
IF((OFF(I).EQ.1.0) .AND. (ABS(EPSXY(I)).GE.eps12f)) THEN
OFF(I) = 0.9999
ENDIF
IF((OFF(I).EQ.1.0 ).AND. (EPSXX(I).GE.eps1f)) THEN
OFF(I) = 0.9999
ENDIF
IF((OFF(I).EQ.1.0 ).AND. (EPSYY(I).GE.eps2f)) THEN
OFF(I) = 0.9999
ENDIF
SIGNXX(I) = SIGNXX(I) * OFF(I)
SIGNYY(I) = SIGNYY(I) * OFF(I)
SIGNXY(I) = SIGNXY(I) * OFF(I)
IF (OFF(I).LT.1.0) THEN
OFF(I) = OFF(I)*0.9
IF (OFF(I).LT.0.1) OFF(I)=0.0
ENDIF
RETURN
END

 Application

Thank you for your attention
RADIOSS
Composite Materials
& Optimization

RADIOSS - Composite Materials & Optimization

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